Systems and applications of lighter-than-air (LTA) platforms

ABSTRACT

Innovative new systems and method of operating the systems, wherein the system comprises an airborne platform comprising an unmanned balloon comprising a gas enclosure; a geographic locator or tracking system configured to determine geographical coordinates of the unmanned balloon; a payload comprising a transceiver, wherein the transceiver is capable of communicating with communication devices that are separate from the unmanned balloon; first and second flight-termination devices each configured to cause termination of a flight of the unmanned balloon; and at least two power sources each configured to provide power to at least one of the first and second flight-termination devices.

RELATED APPLICATIONS

This Application is a Continuation of U.S. patent application Ser. No.15/351,441, filed Nov. 14, 2016 (now U.S. Pat. No. 9,908,608 issued Mar.6, 2018), which is a Continuation-In-Part of U.S. patent applicationSer. No. 14/473,691, filed Aug. 29, 2014 (now U.S. Pat. No. 9,519,045issued Dec. 13, 2016), which is a Divisional of U.S. patent applicationSer. No. 13/757,585, filed Feb. 1, 2013 (now U.S. Pat. No. 8,825,232,issued Sep. 2, 2014), which is a Divisional of U.S. patent applicationSer. No. 12/099,004, filed Apr. 7, 2008 (now abandoned), which is aDivisional of U.S. patent application Ser. No. 10/673,474, filed Sep.30, 2003 (now U.S. Pat. No. 7,356,390, issued Apr. 8, 2008), which is aContinuation-In-Part of U.S. patent application Ser. No. 10/129,666,filed May 9, 2002 (now U.S. Pat. No. 7,203,491, issued Apr. 10, 2007),filed as National Stage of PCT/US02/12228 filed Apr. 18, 2002, whichclaims benefit to U.S. Provisional Application No. 60/284,799 filed Apr.18, 2001; the contents of all of which are incorporated herein in theirentirety by reference.

TECHNICAL FIELD OF THE INVENTION

The present invention relates to unmanned lighter-than-air platformsoperating in the stratosphere and more particularly, their terminationand recovery.

BACKGROUND OF THE INVENTION

Unmanned lighter-than-air ballooncraft have been used for many years toperform tasks such as near space research, and meteorologicalmeasurements. Such ballooncraft have even carried payloads withinstrumentation that sometimes includes radio transmission capabilities.

SUMMARY OF THE INVENTION

Innovative new methods in connection with lighter-than-air free floatingplatforms, of facilitating legal transmitter operation, platform flighttermination when appropriate, environmentally acceptable landing andrecovery of these devices are provided. Especially, termination of radiotransmissions and flight related to regional, governmental andinternational border requirements, regulations and laws. The presentinvention provides methods comprising specific criteria, detection ofthe criteria and elements of operation for reducing or preventingillegal transmissions, for producing rapid descend to the ground, forenvironmentally acceptable landing and for facilitating recovery allwith improved safety and enhanced compliance with known regulations.

BRIEF DESCRIPTION OF THE DRAWINGS

A better understanding of the invention may be had with reference to theattached drawing Figures in connection with the Detailed Descriptionbelow in which like numerals represent like elements and in which:

FIG. 1 schematically depicts a flow diagram of combined methods of atermination decision by a processor including termination criteria,criteria detection by sensing of geographic position and velocity andelements of operation according to certain aspects of the invention;

FIG. 2 schematically depict a mechanism for providing and for releasingballast according to certain aspects of the present invention;

FIG. 3 is a schematic partial front view of a neck of a platformconnecting between a balloon and a payload and depicting theconstruction and method of releasing a balloon from the payloadplatform;

FIG. 4 is a schematic partial front view of the neck of a platformconnecting between a balloon and a payload as in FIG. 3 furtherdepicting the release of the balloon from the payload platform;

FIG. 5 is a schematic diagram for a battery discharge and neck releasecircuit;

FIGS. 6, 7 and 8 are front side and end views, respectively, of a “mapleseed” descent mechanism attached to the bottom of a platform accordingto one embodiment of certain aspects of the invention; and

FIG. 9 is a schematic depiction of a landed terminated platform (withoutballoon) transmitting a locator signal to a floating platformtransceiver that relays the locator information to a ground station tofacilitate recovery of the terminated platform.

DETAILED DESCRIPTION OF THE INVENTION

It has been found that the previous largest use of unmannedlighter-than-air ballooncraft has been by the various weather servicesof the world. For weather data acquisition purposes small latex weatherballoons carry instrument packages called radiosondes to gather theweather data. These weather balloons are launched from a network ofsites around the world at noon and midnight Greenwich Mean Time eachday. The weather service radiosondes collect temperature, humidity,pressure and wind data as they rise from the surface of the Earth toapproximately 100,000 feet during a two-hour flight comprising ascentand rapid descent. At approximately 100,000 feet the weather balloonsburst and the radiosonde payload falls to earth on a parachute. Thisdata acquire during the ascent is input into atmospheric models run onsupercomputers to facilitate predicting the weather. The input data islimited as it represents only a snapshot of the weather data takenduring the balloon ascent every 12 hours. The ascent and decent israpid, mostly within country borders. Also, most countries of the worldare bound by treaty to launch balloon carried radiosondes fromdesignated sites and to share the data with other countries such thatshort duration radio transmissions and physically crossing borders isnot any major issue.

Currently there are about 800,000 radiosondes launched each yearthroughout the world. There are also a small number of radiosondeslaunched for military and research purposes. The research balloonstypically are done using special frequencies and with international orindividual country permission for border crossing. The total numberprimarily represents the 997 global weather stations launching tworadiosondes per day, 365 days per year (727,000). Only about 18% ofthese radiosondes are recovered, reconditioned and reclaimed, resultingin the new production of about 650,000 weather-gathering radiosondes peryear.

The Federal Communications Commission (FCC) prohibits uncontrolledtransmitters as they may cause interference to users on the samefrequency or others on nearby frequencies. FCC spectrum licensesprohibit a US licensed transmitter from transmitting when it leaves theborder of the US.

It has been found that most lighter-than-air platforms that maintainaltitude drop ballast to maintain altitude as lifting gas is lostthrough the balloon membrane that floats the platform. The FederalAviation Administration (FAA) regulations Section 101.7 states thatunmanned ballooncraft are prohibited from dropping objects or operationsuch that a hazard may occur. Sec. 101.7 Hazardous operations.

(a) No person may operate any moored balloon, kite, unmanned rocket, orunmanned free balloon in a manner that creates a hazard to otherpersons, or their property.

(b) No person operating any moored balloon, kite, unmanned rocket, orunmanned free balloon may allow an object to be dropped there from, ifsuch action creates a hazard to other persons or their property.

(Sec. 6(c), Department of Transportation Act (49 U.S.C. 1655(c)) [Doc.No. 12800, Arndt. 101-4, 39 FR 22252, Jun. 21, 1974]

A major factor influencing the size and cost of a lighter-than-airplatform is the weight of the payload. For small ballooncraft such asweather balloons, they may become exempt from certain FAA reporting,lighting, and launching requirements if the total payload weight is keptbelow 6 pounds and a density of 3 ounces or less per square inch of thesmallest side. Sec.101.1 (4)Applicability.

(a) This part prescribes rules governing the operation in the UnitedStates, of the following:

(4) Except as provided for in Sec. 101.7, any unmanned free balloonthat—

(i) Carries a payload package that weighs more than four pounds and hasa weight/size ratio of more than three ounces per square inch on anysurface of the package, determined by dividing the total weight inounces of the payload package by the area in square inches of itssmallest surface;

(ii) Carries a payload package that weighs more than six pounds;

[Doc. No. 1580,28 FR 6721, Jun. 29, 1963, as amended by Arndt. 101-1, 29FR 46, Jan. 3, 1964; Arndt. 101-3, 35 FR 8213, May 26, 1970]

The unique use of a low-density payload also significantly reduces costsassociated with the launch and allows a launch to occur in all weatherconditions. The amount of ballast required to keep a platform within aset altitude range over a 24-hour period is typically on the order of15% of the total system weight. This is a significant percentage of thetotal weight for a floating platform or ballooncraft mission lastingover multiple days. For example, it has been found that a three dayflight may require that 38% of the platform's system weight be ballast.This either significantly increases the size of the balloon or decreasesthe weight available for the payload.

The two sections of the FAA regulations above show the FAA's concernwith increased payload weights and increased densities. This appears tofocus on reducing the potential for damage to an aircraft in acollision. The density and total weight of the payload are also found tobe significant factors in overall safety upon the payload's return tothe earth. Generally lower weight and density payloads, are believed toreduced chances of causing physical damage, and as a beneficial resultmay also be easier and less costly to insure as well.

The FAA further prohibits uncontrolled lighter-than-air balloons. Againthere may be a concern that uncontrolled flight may present a hazard toaircraft. For example, in 1998, a large uncontrolled scientific balloonlaunched by the Canadian Space Agency prompted re-routing oftrans-Atlantic passenger flights for 10 days as it drifted from itslaunch site in Canada until it finally landed in Finland. Theuncontrolled balloon also resulted in aviation concerns in Russia andNorway. Significant resources were expended, including the use offighter jets to try to bring the uncontrolled balloon down.

Until now, unmanned, free drifting, lighter-than-air balloons have beeneither restricted to short flights as is the case with the 50,000 NWSweather balloons launched each year, or a very few large and expensivelong duration scientific flights. The NWS weather balloons have anextremely limited life (approximately 2 hours) and their transmittersand batteries have limited power. The long duration scientific balloonstypically have long lives and extended missions. These infrequentballooncraft flights are expensive and generally require frequency andsafety coordination with each country that they overfly. They may gainauthorization to use government or scientific frequencies for shortperiods of time that are not available for commercial users.

Applicants, as disclosed in a co-pending application, have discoveredand developed new and commercially viable uses for small free-floatingplatforms with long duration capabilities. These small, long durationballooncraft or free floating platforms have long flight lives similarto much larger scientific ballooncraft and the ability to travel longdistances. The present methods and inventive devices facilitate avoidingthe massive reporting and coordination requirements of the largerballooncraft. The free-floating platforms may be operating on commercialfrequencies that have specific laws as to the use of the frequencies ineach country. The innovative new methods facilitate maintenance of legaltransmitter operations, particularly at borders, they provide forplatform flight termination for rogue, uncontrolled or malfunctioningplatforms, they provide for environmentally acceptable descent and theyenhance the opportunity for recovery and reuse of these devices. All ofthese methods are especially useful as they relate to regional andinternational borders. The present invention uses specific criteria andelements of operation or sets of criteria and elements of operation thattaken as a whole form a safe method for reducing or preventing illegaltransmissions, for terminating flight, for rapidly descending theplatform to the ground, for environmentally acceptable landing and forenhanced recovery. All the methods are designed to enhance safety and tocomply with known regulations.

FIG. 1 schematically depicts a flow diagram of combined methods of atermination decision by a processor including termination criteria,criteria detection by sensing of geographic position and velocity, andelements of operation according to certain aspects of the invention. Incombination with an onboard power source 12 and GPS 14 (or othergeographic locator or tracking system), a processor 10 is provided toreceive position information and time change of position (velocity)information 14. The position information is compared to stored orprogrammed criteria information at 16, 18, 20, 22, 24, 26, 28 and 30, todetermine whether termination of radio transmission and/or terminationof flight should be implemented.

The following criteria based decisions are provided with the processor10:

Has the platform moved or drifted outside of a certain geographic area?(See FIG. 1, at 16.)

The relevant boundaries may be frequency license borders set by the FCCas dictated by a regional or nationwide broadcasting license. The FCCprohibits transmitter operation outside such geographic borders.Additionally, a neighboring country may have restrictions on transmittedpower into their country from a United States transmitter. It has beenfound that on certain frequencies Mexico prohibits transmit power levelsabove −99 dBm into Mexico from the United States. These restrictions arenot hard for terrestrial towers as they can use directional antennasonce during installation and not have to adjust them again thereafter.This is quite different for a free drifting high altitude ballooncraftas the position and altitude may be constantly changing and may requirethe platform to stop transmitting while still inside the United States,but within a protective number of miles of the United States-Mexicoborder. Long duration scientific ballooncraft are not as concerned withthis as they typically work on special frequencies or have coordinatedwith other countries that may be over flown.

Is the platform moving outside of boundaries that would significantlyreduce the probability of recovering the platform? (See FIG. 1 at 18.)

As payloads costs may be significant, from $50 to $150 for a typicalweather service radiosonde, up to hundreds of dollars for a transceiverplatform, and up to many tens of thousands of dollars for a scientificpayload, recovery is important both financially and for environmentalreasons. A platform may encounter strong winds especially in the jetstream as it descends from high altitudes. In order to keep the platformfrom drifting out of the country on descent, artificial borders thattake into account the winds during descent can be used. Also, boundariesof large bodies of water such as the great lakes, seas and oceans thecrossing of which might hamper or prevent recovery of the platform uponnormal decent, may be taken into account for termination of flightpurposes.

Has the platform fallen below or risen above a set altitude range? (SeeFIG. 1 at 20)

Most scientific and weather balloons reach altitudes above 60,000 feet,The FAA regulates airspace below 60,000 feet and discourages freefloating craft or uncontrolled flight craft from loitering especially incommercial air lanes as they present a hazard to commercial planes.Current NWS weather balloons do not have the capability to terminate theflight if they start to hover below 60,000 feet. Even the large-scalescientific balloons may become errant and free drift below 60,000 feet.(see the rogue scientific balloon example listed earlier). There is astrong need for a ballooncraft to terminate it's flight if it is not inthe proper altitude range.

Is the platform velocity sufficient to create an unacceptably largeDoppler shift in the transmission frequency? (See FIG. 1, at 22)

A ballooncraft traveling in the jet stream may reach speeds of over 180miles per hour. This creates a Doppler shift in the frequencies receivedon the ground. The FCC regulates the amount of total frequency driftallowed on a commercial transmission. Doppler shift contributes to thistotal frequency drift and if great enough can cause the transmitter totransmit out of its allowed band. These requirements have not beenconsidered or accounted for in the past as free drifting commerciallytransmitting platforms were not available. Therefore, the requirementthat the payload be able to immediately stop transmitting past the speedat which the Doppler becomes too great is new.

Does the platform fall rate indicate a balloon burst? (See FIG. 1, at24.)

A fast fall rate indicates that the balloon has burst and that the craftis falling. The transmission of radio signals should be terminated andthe other termination actions should be promptly initiated.

Is the lighter-than-air platform rising too slow? (See FIG. 1, at 26.)

This indicates that the balloon is under-filled or leaking. A slow riserate may present a danger to aircraft by loitering excessively at onealtitude particularly at an altitude in designated air lanes.

Has the processor, the position finding equipment, or the primary powerfailed? (See FIG. 1, at 28.)

A GPS, star tracker, or system power failure will cause an on-boardtermination. The platform must be able to terminate without processorcontrol or power.

Have command and control communications been lost? (See FIG. 1, at 30.)Without command and control from the ground, the payload should ceasetransmission and the flight must should be terminate.

The present inventive system detects the foregoing conditions bycomparing current position, velocity, and operating conditions tostored, programmed or calculated criteria using an onboard processor.The present invention utilizes a GPS unit and a processor to determinethe current platform's geographic coordinates and velocities. A GPS unitor pressure sensor determines the platform altitude. The processoralgorithms will implement the complete set of conditions listed abovecausing the ballast to be released at 34, the transmitter to be shut offat 38 and the flight terminated at 36 upon detection of a stored,programmed or calculated termination criteria. Under conditions of apower loss or processor failure, the transmitter will also be shut offat 38, and the flight will be terminated at 36. The methods andmechanisms for the termination actions are described more fully below.

A separate termination controller 11 under separate power 13 monitorsthe primary platform power at 32 and monitors processor functions at 30to determine if the processor 10 is functioning properly. Both theprimary processor 10 and the separate termination controller 11 have theability to terminate transmissions, by discharging the primary platformbatteries at 38 and to terminate the flight by releasing the balloon at36. The separate power source 13 may advantageously comprise a verysmall environmentally acceptable battery such as an alkaline watchbattery.

The present invention solves certain past needs. This inventiondescribes a system, method and design for use with lighter-than-airplatforms that overcomes certain safety drawbacks of conventionalunmanned lighter-than-air ballooncraft. The processor reduces oreliminates the chance of the platform becoming a free floating,uncontrolled transmitter by monitoring sensed coordinates and platformvelocities (GPS, star tracker, etc) and by comparing the sensedinformation to known (stored, programmed or calculated) geographic oraltitude based boundaries. If the processor determines that the platformis out of its proper boundaries, termination is started. If the GPSfails, the processor also initiates termination. If the processorfunction unacceptably fails or if the primary power fails, terminationand recovery is also automatically initiated with a secondarytermination control circuit having its own small and environmentallyacceptable power source. This does not require power from the primarypower source of the platform.

Termination and recovery comprise several steps or actions as follows:

Releasing all ballast to reduce the payload density and weight. Attermination, all ballast is released automatically according to amechanism as schematically depicted in FIG. 2. Ballast system andrelease mechanism

Both reactant A in Chamber A (100) and reactant B in Chamber B (101) ismetered into the reaction chamber (104) where hydrogen generationoccurs. The relative size of each of the two chambers is determined bythe molar ratio of the reaction. If water is used as one of thereactants and a fuel cell is used on the platform for generating power,the water byproduct of the fuel cell's reaction may be used for theballast system reaction as one of the reactants. Different meteringrates would be required for each reactant if the molar ratio of thereactants were not 1 to 1. This could be done with a dual peristalsispump (102) if the tubing diameters were adjusted to pump the appropriateamount from each reactant chamber. During the reaction, hydrogen isvented from the reaction chamber through a tube (107) into the balloon.A one-way valve (106) in the tube to the balloon prevents hydrogen fromflowing back into the reaction chamber. After the reaction is complete,the byproduct is dropped as ballast from the bottom of the reactionchamber (104) through an electrically actuated valve (105). The valve(105) is then closed. Unless the balloon has burst, upon flighttermination, the reactants will be reacted as quickly as safely possiblein the reaction chamber (104) and the byproducts dropped as ballast. Ifthe balloon has burst, the pumps may not be to pump as effectively fromthe chambers unless the chambers have a slight pressure and no air isallowed in them.

In a second configuration (not depicted), the ballast system comprisestwo cavities each containing one of the two reactants. The reactant inthe top cavity is metered into the lower cavity where the hydrogengeneration occurs. The reaction byproducts are only released as ballastwhen all of the original reactants are depleted.

This makes the payload lighter and therefore safer in the event ofcollision with aircraft or persons and property on the ground. While anyacceptable ballast could be released, the novel ballast system describedabove effectively reduces the actual weight of ballast required by asystem thereby increasing the safety of the payload. In the novelballast system the total amount of ballast carried to provide longduration flight at an acceptable altitude is significantly reduced.Reducing the amount of ballast should in most cases increase safety. Inone specific example, the system uses water and either Sodium Hydride orCalcium Hydride as the ballast. When additional altitude is required, aquantity of water is added to a quantity of Sodium Hydride or CalciumHydride. A large volume of hydrogen gas is generated. This hydrogen isadded to the lifting balloon and the byproducts of the reaction aredropped as ballast. The platform becomes lighter due to the dropping ofthe Ca(OH)2 or Na(OH)2 byproduct and at the same time, hydrogen is addedto the balloon increasing lift. Only 73% (75% for Sodium Hydride) of anequivalent weight of inert ballast such as sand is needed. As ballastcan be a significant portion of the initial total weight, reducing theweight of the ballast significantly reduces the total weight of thepayload.

Releasing the neck of the balloon from the platform to initiate a quickdescent.

This makes sure the platform descends quickly through the atmospherethereby reducing the potential time through the commercial air lanes.Small balloon systems such as the NWS weather balloons rely on theballoon bursting due to expansion as it rises through the atmosphere. Ahovering balloon does not experience this expansion and therefore musteither have a system to burst the balloon or physically separate fromthe balloon. Venting the balloon is generally not acceptable because ofthe danger of the balloon drifting laterally on the ground increases thechance of personal or property damage. A further problem would occur ifhydrogen was used as the lifting gas. This could create a possibility ofhydrogen remaining in the balloon after landing and becoming a potentialignition source. Bursting the balloon is also less desirable as theburst balloon still attached to the payload may foul the descentmechanism causing an uncontrolled descent. In the invention, the neck ofthe ballooncraft is released when power is lost or the processor fails.

One possible implementation of the neck release mechanism as depictedschematically in FIGS. 3 and 4, comprises two concentric neck connectiontubes (43) and (49). The top tube (43) is attached to the balloon (41)with a strap (42) or rubber band (42) and fits within the bottom tube(49), which is attached to the payload (51). The top tube (43) isrestrained from sliding out of the bottom tube (49) by a piece ofmonofilament line (47). While top tube (43) and bottom tube (49) arerestrained to each other, flexible seal (44) prevents gas in the tubesfrom leaking at the junction of the tubes. Each end of the monofilamentline (47) is threaded through a small hole in flange (46) and tied off.The monofilament line (47) is threaded around two knobs (52) and alsothrough and in contact with an electrically resistive coil (48).

When thermination of the flight is called for, the ballast is preferablyreleased first and then a discharge circuit passes current through theresistive coil (48). The coil heats (48) up and melts through themonofilament line (47). The weight of the payload (51) now pulls thebottom tube (49) from the top tube and the payload is released from toptube (43).and thus from the balloon (41). This ballast systemadvantageously allows for the venting of the lifting gas directly at thepayload eliminating the need for wiring to remote valves. Integration ofthe actuator electronics simplifies the design and ultimately thereliability of the platform.

The battery discharge and neck release circuit is schematically depictedin FIG. 5. The processor must constantly supply a keep alive signal tothe battery discharge circuit in order to prevent the batteries fromdischarging. This keep alive signal consists of a square wave. Thebattery discharge circuit senses the low to high transitions in the keepalive signal and resets the timer (a HEF 4060) each time the transitionis detected. The timer must be reset by the presence of the keep alivesquare wave or the timer will end it's counting and initiate the batterydischarge. A high power FET closes the circuit that discharges thebatteries. In one implementation of the discharge circuit, the powerfrom the discharge circuit comes from the main batteries themselves.Because the discharge circuitry can function down to extremely lowbattery voltages, the batteries are effectively discharged by the timethe discharge circuit is unable to function.

An alternate implementation uses a separate, non-hazardous, smallbattery to operate the discharge circuitry. This implementation ensuresthat the main batteries are completely discharged. The discharge circuitdissipates power through the resistive wire that during batterydischarge, dissipates the energy as heat. The resistive wire is wrappedaround a piece of monofilament (fishing) line. When the battery power isdissipated through the resistive wire, the monofilament line is meltedthrough and the neck connecting the balloon to the platform is releasedfrom the payload. Another advantage of providing a separate power sourcefor the discharge circuit is that the discharge circuit battery willsupply the resistive element with power to cut the monofilament lineeven if the main batteries are dead. As an alternative, the dischargecircuit could dissipate power through a high power resistor if the neckrelease function were not used.

If the processor senses any of the conditions necessary to initiatetermination, it ceases sending the keep alive signal to the dischargecircuit. If the processor dies or the power fails, the keep alive signalalso ceases, causing termination. The timer advances to a point where itinitiates the battery discharge. Battery current flows through theresistive wire discharging the batteries and melting through themonofilament to release the balloon neck. The battery dischargecontinues until the main batteries are completely dead.

The main platform batteries are fully discharged during descent and ifneeded upon landing to positively terminate and prevent further radiotransmission. Once discharge is initiated, the batteries fully dischargeeliminating the chance of transmitting with significant power. Thebattery discharge can be initiated by the processor as described aboveor automatically when power or processor control is lost. It has beenfound that long duration platform flight at high altitudes and coldtemperatures requires special high-density power and functionalcapabilities at low temperatures. It has been found that lithiumbatteries beneficially fulfill such requirements. Additionally, it wasfound that the Environmental Protection Agency (EPA) states that lithiumbased batteries are considered hazardous waste except for one type ofcell and only when fully discharged. Particularly it has been found thatLithium Sulfur Dioxide (LiS02) batteries, when fully discharged, form alithium salt, which is not considered hazardous by the EPA.Automatically discharging the LiS02 batteries before they contact theground not only prevents the transmitter from transmitting but alsorenders the batteries non-hazardous for environmentally acceptablelanding on the ground.

Use of a novel and integral “maple seed” like descent device to increasesafety is depicted in FIGS. 6, 7 and 8. A single airfoil shaped bladeattached to the bottom of the platform causes autorotation of thepayload and airfoil blade upon rapid descent. This replaces atraditional parachute with a highly reliable decelerator that isgenerally immune to fouling than a parachute and less complex. Nodeployment mechanism is necessary and it is immune to the foulingproblems with animals after descent. The “maple seed” decelerator mayalso be used to conveniently house the platform antenna.

A novel method of platform recovery is depicted in FIG. 9. To aid in therecovery of the platform, the landed platform sends its last recordedposition to an additional airborne platform using a low powertransmitter and tiny battery. The transmitter might utilize one of thelow power unlicensed bands to send the information. The second platformrelays the current location of the landed platform to the ground stationto aid in recovery.

What is claimed is:
 1. A system comprising: an airborne platformcomprising a balloon comprising a gas enclosure, wherein the balloon isan unmanned balloon; a GPS unit configured to determine geographiccoordinates and velocities of the airborne platform; a pressure sensorconfigured to determine an altitude of the airborne platform; aprocessor, wherein the processor comprises an algorithm to determinewhether to release a ballast based on a set of termination criteria; aballast release mechanism configured to release the ballast; and a neckrelease mechanism configured to release a payload, wherein the systemcomprises a first flight termination device and a second flighttermination device, wherein each of the first flight termination deviceand the second flight termination device is configured to causetermination of a flight of the airborne platform and has at least twopower sources each configured to provide power to at least one of thefirst flight termination device and the second flight terminationdevice.
 2. The system of claim 1, wherein the set of terminationcriteria are: platform outside geographic boundaries; platform outsiderecovery boundaries; altitude outside of legal range; lateral velocitysuch that Doppler is greater than acceptable limits; falling velocityabove limits indicating the balloon burst; climbing velocity belowlimits indicating under filled or leaking or loitering balloon; commandand control link with a ground station is lost for greater thanallowable time; processor failure; and a power loss.
 3. The system ofclaim 1, wherein the processor checks the set of termination criteria bycomparing current position, velocity, and operating conditions tostored, programmed or calculated criteria.
 4. The system of claim 1,wherein the algorithm checks for all of the criteria listed as the setof termination criteria in claim 3 and if any one criterion is satisfiedcauses the ballast to be preferably released first followed by thepayload release through the neck release mechanism.
 5. The system ofclaim 1, wherein the release mechanism is configured to release one ormore components from the payload and a released component descends undergravity or on a recovery system.
 6. The system of claim 5, wherein therecovery system for recovering the airborne platform is a parachute. 7.The system of claim 5, wherein the recovery system for recovering theairborne platform is a maple-leaf recovery system.
 8. The system ofclaim 5, wherein the recovery system for recovering the airborneplatform houses an antenna configured to send a last recorded positionof the airborne platform to another airborne platform.
 9. The system ofclaim 1, wherein the ballast release mechanism comprising: two chambersto hold two different reactants; a metering pump; a reaction chamber; anelectrically actuated valve; and a venting tube incorporated with aone-way valve.
 10. The system of claim 9, wherein size of the twochambers that are configured hold the reactants is determined based on amolar ratio of a reaction between the two different reactants.
 11. Thesystem of claim 9, wherein the metering pump is a dual peristalsis pump.12. The system of claim 9, wherein the two different reactants react toproduce hydrogen in the reaction chamber.
 13. The system of claim 9,wherein the electrically actuated valve is actuated to release theby-products produced in the reaction chamber as the ballast.
 14. Thesystem of claim 9, wherein the one-way valve of the venting tube isconfigured to vent the hydrogen to the balloon of the airborne platform.15. The system of claim 1, wherein the neck release mechanismcomprising: two concentric tubes forming a neck connection wherein a toptube is attached to the airborne platform with a strap or a rubber bandand fits within a bottom tube attached to the payload; a restrainingmechanism for the top tube to prevent from sliding out of the bottomtube by a monofilament line; a flexible seal to prevent gas from leakingat a junction formed from the top tube and the bottom tube.
 16. Thesystem of claim 15, where in each end of the monofilament line isthreaded through a small hole in flange and tied off and is threadedaround two knobs and also through and in contact with an electricallyresistive coil.
 17. The system of claim 16, where in the monofilamentline is configured to melt when the electrically resistive coil isheated up and thus releasing the bottom tube attached to the payloadfrom the top tube attached to the airborne platform or a balloon.
 18. Adevice comprising: two chambers to hold two different reactants; ametering pump; a reaction chamber; an electrically actuated valve; and aventing tube incorporated with a one-way valve, wherein the device isconfigured to release a ballast.
 19. The device of claim 18, whereinsize of the two chambers that are configured to hold reactants isdetermined based on a molar ratio of a reaction between the twodifferent reactants.
 20. The device of claim 18, wherein the meteringpump is a dual peristalsis pump.
 21. The device of claim 18, wherein thetwo different reactants react to produce hydrogen in the reactionchamber.
 22. The device of claim 18, wherein the one-way valve of theventing tube is configured to vent the hydrogen to the balloon of theairborne platform.
 23. The device of claim 18, wherein the electricallyactuated valve is actuated to release the by-products produced in thereaction chamber as the ballast.
 24. A device comprising: two concentrictubes forming a neck connection wherein a top tube is attached to anairborne platform with a strap or a rubber band and fits within a bottomtube attached to a payload; a restraining mechanism for top tube toprevent from sliding out of the bottom tube by a monofilament line; aflexible seal to prevent gas from leaking at a junction formed from thetop tube and the bottom tube, wherein the device is configured torelease the payload from a balloon neck.
 25. The device of claim 24,where in each end of the monofilament line is threaded through a smallhole in flange and tied off and is threaded around two knobs and alsothrough and in contact with an electrically resistive coil.
 26. Thedevice of claim 25, where in the monofilament line is configured to meltwhen the electrically resistive coil is heated up and thus releasing thebottom tube attached to the payload from the top tube attached to theairborne platform or the balloon.
 27. A system comprising an airborneplatform comprising an unmanned balloon comprising a gas enclosure; ageographic locator or tracking system configured to determinegeographical coordinates of the unmanned balloon; a payload comprising atransceiver, wherein the transceiver is capable of communicating withcommunication devices that are separate from the unmanned balloon; firstand second flight-termination devices each configured to causetermination of a flight of the unmanned balloon; at least two powersources each configured to provide power to at least one of the firstand second flight-termination devices; a payload release mechanism; anda recovery mechanism.